A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

A first component, such as a hub of a gas turbine engine is assembled or disassembled from a second component, such as a shaft by induction heating, using a flexible heating jacket that is wrapped about an outer circumferential surface of the hub. The jacket includes an electrically conductive, flexible cable, having a plurality of loops. The jacket is selectively opened and closed with a plurality of electrical connectors coupled to each respective loop of the cable. A power source passes current through the respective cable loops, which heats the hub. The induction heating is applied to the mating components in the engine, in order to create a sufficient temperature differential that permits assembly or disassembly of the hub and shaft. A controller regulates power applied to the hub and shaft and monitors their temperature with temperature sensors.

The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).

A weldment includes a first component, a second component, and a weld joint coupling the first and second components together. The weld joint forms a heat affected zone in the first component and creates residual tensile stress in the first component. The first and second components cooperate to define a pocket configured to position a highest magnitude of the residual tensile stress in the first component in a location that is outside of the heat affected zone of the first component.

A rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically to the rotor axis inside the rotor shaft. The rotor shaft further includes a plurality of cooling bores extending radially outward from the rotor cavity to feed cooling air into an internal cooling system in a blade. Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portion ends in a plateau, projecting above the outer circumference contour of the rotor cavity. Thus, cooling bore inlets are shifted to a low stress area and the lifetime of the rotor is improved.

A rotor shaft for a turbine rotor of a turbine, in particular a steam turbine, having a shaft main body made of a first material and at least one ring which is made of a second material and is attached to the shaft main body, wherein the second material has equal or greater strength and/or greater corrosion resistance than the first material, wherein at least one blade slot is formed on the ring, and wherein the ring is materially bonded to the shaft main body by narrow-gap welding.

A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

According to an embodiment, a method of correcting a bend of a joint type-turbine rotor comprises: measuring displacement of a convex portion of the bend at a joined portion of the joint type-turbine rotor or displacement of a surface opposite to the convex portion in a circumferential direction of the joint type-turbine rotor; heating the convex portion; and cooling the joined portion after the step of heating. The steps of heating and cooling are performed during the step of measuring.

The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).

A method for welding a first powder metallurgical (PM) part to a second powder metallurgical (PM) part includes: working a first face of the first PM part; working a first face of the second PM part; and friction welding the first face of the first part to the first face of the second part.